Quiet aerial vehicle

ABSTRACT

An aerial vehicle including a main body having a leading edge. An inlet is recessed aft from the leading edge. Forward protrusions extend from the main body on opposite sides of the inlet. An outlet nozzle is proximate to an aft end. The inlet is in fluid communication with the outlet nozzle. Wings extend from the main body.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application relates to and claims priority benefits from U.S.Provisional Application No. 63/074,650, entitled “Quiet Unmanned AerialVehicle Configuration,” filed Sep. 4, 2020, which is hereby incorporatedby reference in its entirety.

This application is also a continuation-in-part of U.S. Design patentapplication Ser. No. 29/749,405, entitled “Aerial Vehicle,” filed Sep.4, 2020, which is hereby incorporated by reference in its entirety.

FIELD OF THE DISCLOSURE

Embodiments of the subject disclosure relate to unmanned aerial vehicles(UAVs), and more particularly to an aerial vehicle that is configured toreduce propagation of noise to ground observers.

BACKGROUND OF THE DISCLOSURE

Aerial vehicles can be used for remote monitoring or surveying. Forexamples, missions for air vehicles include surveying of wildlife,reconnaissance of potentially hostile environments, and the like. UAVsare a subset of such vehicles.

Conventional UAVs typically include motors having un-ducted fans thatgenerate noise that propagates in all directions and can allow earlydetection of the UAV from the ground from far distances. The detectionof fan noise can result in reduced monitoring effectiveness due to thedetection of the UAV.

SUMMARY OF THE DISCLOSURE

A need exists for an aerial vehicle, such as a UAV, that generates lessnoise than known UAVs. Further, a need exists for an aerial vehicle thatquietly operates with reduced acoustic transmissions to the groundbelow.

With those needs in mind, certain embodiments of the subject disclosureprovide an aerial vehicle including a main body having a leading edge.An inlet is recessed aft from the leading edge. Forward protrusionsextend from the main body on opposite sides of the inlet. An outletnozzle is proximate to an aft end of the main body. The inlet is influid communication with the outlet nozzle. Wings extend from the mainbody. In at least one embodiment, the aerial vehicle is an unmannedaerial vehicle (UAV).

In at least one embodiment, the main body includes a base having a flatforward upper surface. The inlet extends upwardly from the flat forwardupper surface.

In at least one embodiment, the aerial vehicle also includes canardsextending from a fore end of the main body. The wings extend from theaft end of the main body. As a further example, at least portions of thecanards extend to a plane that is aft of the inlet.

In at least on embodiment, at least one of the forward protrusionsextends either above or below a height of the inlet. In at least onexample, the forward protrusions form a funneling entrance to the inlet.

In at least one embodiment, the inlet has a width and a height. Anaspect ratio is defined as a ratio of the width to the height. Theaspect ratio is between 3 and 7. For example, the aspect ratio isbetween 4.9 and 5.1.

In at least one embodiment, the inlet is recessed from the leading edgea distance that is between 1 to 5 times a height of the inlet. Forexample, the distance is between 2.9 and 3.0 times the height of theinlet.

In at least one embodiment, the aerial vehicle also includes an inletduct within the main body. The the inlet provides an opening into theinlet duct. A propulsor is within the main body and in fluidcommunication with the inlet duct. An outlet duct is within the mainbody and in fluid communication with the propulsor. The outlet ductincludes the outlet nozzle.

Certain embodiments of the present disclosure provide a method offorming an aerial vehicle. The method includes recessing an inlet aftfrom a leading edge of a main body; extending forward protrusions fromthe main body on opposite sides of the inlet; fluidly coupling an outletnozzle proximate to an aft end of the main body to the inlet; andextending wings from the main body.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 illustrates a perspective top view of an aerial vehicle,according to an embodiment of the subject disclosure.

FIG. 2 illustrates a top view of the aerial vehicle.

FIG. 3 illustrates a bottom view of the aerial vehicle.

FIG. 4 illustrates a first lateral view of the aerial vehicle.

FIG. 5 illustrates a second lateral view of the aerial vehicle.

FIG. 6 illustrates a front view of the aerial vehicle.

FIG. 7 illustrates a rear view of the aerial vehicle.

FIG. 8 illustrates a top transparent view of the aerial vehicle.

FIG. 9 illustrates a lateral transparent view of the aerial vehicle.

FIG. 10 illustrates a cross-sectional view of the aerial vehicle throughline 10-10 of FIG. 2.

FIG. 11 illustrates a cross-sectional view of the aerial vehicle throughline 11-11 of FIG. 2.

FIG. 12 illustrates a cross-sectional view of the aerial vehicle throughline 12-12 of FIG. 2.

FIG. 13 illustrates a flow chart of a method of forming an aerialvehicle, according to an embodiment of the subject disclosure.

DETAILED DESCRIPTION OF THE DISCLOSURE

The foregoing summary, as well as the following detailed description ofcertain embodiments will be better understood when read in conjunctionwith the appended drawings. As used herein, an element or step recitedin the singular and preceded by the word “a” or “an” should beunderstood as not necessarily excluding the plural of the elements orsteps. Further, references to “one embodiment” are not intended to beinterpreted as excluding the existence of additional embodiments thatalso incorporate the recited features. Moreover, unless explicitlystated to the contrary, embodiments “comprising” or “having” an elementor a plurality of elements having a particular condition can includeadditional elements not having that condition.

FIG. 1 illustrates a perspective top view of an aerial vehicle 100,according to an embodiment of the subject disclosure. FIG. 2 illustratesa top view of the aerial vehicle 100. FIG. 3 illustrates a bottom viewof the aerial vehicle 100. FIG. 4 illustrates a first lateral view ofthe aerial vehicle 100. FIG. 5 illustrates a second lateral view of theaerial vehicle 100. FIG. 6 illustrates a front view of the aerialvehicle 100. FIG. 7 illustrates a rear view of the aerial vehicle 100.Referring to FIGS. 1-7, in at least one embodiment, the aerial vehicle100 is an unmanned aerial vehicle (UAV), such as a drone. Optionally,the aerial vehicle 100 can include a cockpit, flight deck, and/orinternal cabin that is configured to support a pilot, flight crew, oneor more passengers, and/or the like.

The aerial vehicle 100 includes a main body or fuselage 102. The mainbody 102 extends from a fore end 104 to an aft end 106. The main body102 includes a base 108 that connects to lateral walls 110 and a topwall 112. The lateral walls 110 can be outwardly bowed. For example, thelateral walls 110 can outwardly curve toward a central plane 114 andinwardly curve from the central plane 114 toward the base 108 and thetop wall 112. One or both of the base 108 and the top wall 112 includesa flat surface. For example, the top wall 112 includes a flat uppersurface 116. The flat upper surface 116 can be parallel to the centralplane 114. Similarly, the base 108 can include a flat lower surface 117.The flat upper surface 116 and the flat lower surface 117 of the base108 provides a flattened body. Alternatively, the base 108 and the topwall 112 may not include flat surfaces.

Wings 118 outwardly extend from the main body 102. As shown, the wings118 extend laterally from the main body 102 proximate to the aft end106. The wings 118 include roots 120 that connect to portions of thelateral walls 110 and the top wall 112, such as at the aft end. Asshown, the roots 120 may not extend to a central longitudinal axis 122.The roots 120 connect to extensions 124 that extend outwardly andlaterally away from the main body 102. The extensions 124 includeleading edges 126 and trailing edges 128. Control surfaces 130 aredisposed on the extensions 124, such as at the trailing edges 128. In atleast one embodiment, the wings 118 rearwardly angle from the roots 120to distal edges 132. Further, vertical stabilizers 134 can extend fromthe distal edges 132. The vertical stabilizers 134 can inwardly anglefrom lower edges 135 toward upward edges 137.

Canards 136 extend from the fore end 104 of the main body 102. Forexample, the canards 136 extend from the base 108 and/or the lateralwalls 110 at the fore end 104. As shown, the canards 136 extend from themain body 102 at the fore end 104, and the wings 118 extend from themain body 102 at the aft end 106. The canards 136 can be disposed inplanes that are below the planes of the extensions 124 of the wings 118.

An inlet 138 is formed in the main body 102 at the fore end 104. Theinlet 138 can be aft of leading edges of the canards 136. The canards136 are in front and to the sides of the inlet 138. The inlet 138 is anopening formed in the main body 102 between the base 108 and the topwall 112. In at least one embodiment, the inlet 138 is aligned with thecentral longitudinal axis 122 of the main body 102. In at least oneembodiment, as shown in FIG. 2, in particular, the inlet 138 extendsupwardly from the flat forward upper surface 109 of the base 108.

The canards 136 define a canard leading edge 141. In at least oneembodiment, the canard leading edge 141 joins to the main body 102 atthe leading edge 146. In at least one embodiment, the canards 136 can beconfigured such that root chords 143 of the canards 136 extend from theleading edge 146 to a plane 151 that is aft of the inlet 138. That is,aft edges 149 of the canards 136 extend to a distance that is behind aplane 133 in which the inlet 138 resides. It has been found thatplacement of the canards 136 a distance aft of the inlet 138 providessecondary shielding of any acoustic emanations form the inlet 138.

Forward protrusions 142 forwardly extend from the main body 102. Theforward protrusions 142 bound opposite sides 121 and 123 of the inlet138, which is recessed from the leading edge 146 of the aerial vehicle100. The forward protrusions 142 extend forwardly from the main body 102on the opposite sides 121 and 123 of the inlet 138.

The forward protrusions 142 extend forward and laterally past the inlet138. The forward protrusions 142 can extend above and/or below a height144 of the inlet 138. The forward protrusions 142 can extend to aleading edge 146 of the aerial vehicle 100. In at least one embodiment,the forward protrusions 142 extend toward, but not to, the leading edge146. For example, forward ends of the forward protrusions 142 can be setback from the leading edge 146.

In at least one embodiment, the forward protrusions 142 extend forwardlyfrom the inlet 138 a distance that is between 1-3 times the distance ofthe height 144 of the inlet 138, thereby forming a funneling entrance139, such as U-shaped entrance, to the inlet 138. The funneling entrance139 directs airflow into the inlet 138 as the aerial vehicle 100 flies.Moreover, the forward protrusions 142 help direct sound generated withinthe main body 102 upwards by providing reflective surfaces that directacoustic waves upwardly (in contrast to the ground).

The height 144 of the inlet 138 extends from the base 108 to a lowerfront edge 113 of the top wall 112. In at least one embodiment, theinlet 138 is a high aspect ratio inlet, where aspect ratio is defined asthe width 147 to the height 144 of the inlet 138. For example, acircular inlet, similar to most inlets on commercial airliners, wouldhave an aspect ratio of 1. In at least one embodiment of the subjectdisclosure, however, the aspect ratio of the inlet 138 is between 3 and7. For example, the aspect ratio of the inlet 138 is between 4.9 and5.1. In at least one embodiment, the aspect ratio of the inlet 138 isbetween 4 and 6. For example, the aspect ratio is 5.

In at least one embodiment, the inlet 138 is recessed aft from theleading edge 146 of the aerial vehicle 100. Displacing the inlet 138 aftfrom the leading edge 146, in conjunction with the flattened main body102 shields, dampens, or otherwise reduces sound emanating from withinthe inlet 138. In particular, the recessed inlet 138 and flattened mainbody 102 reflects generated noise upwardly, in contrast to propagatingnoise downwardly toward the ground. In at least one embodiment, theinlet 138 is recessed from the leading edge 146 a distance that isbetween 1 to 5 times the height 144 of the inlet 138. In at least oneembodiment, the inlet 138 is recessed from the leading edge 146 adistance that is between 2.9 and 3.0 times the height of the inlet 138.It has been found that such a distance (as may be in conjunction withthe flattened main body 102) effectively propagates generated noiseupwardly, in contrast to downwardly toward the ground.

In at least one embodiment, the inlet 138 is set back from the leadingedge 146 of the aerial vehicle 100 a distance 148 that is between 2.5and 3.5 times the height 144 of the inlet 138. For example, the inlet138 is set back from the leading edge 146 a distance that is 2.95 timesthe height 144.

FIG. 8 illustrates a top transparent view of the aerial vehicle 100. Theinlet 138 fluidly connects to an inlet duct 160 that extends within themain body 102. The inlet duct 160 connects to a propulsor 162 that iswithin the main body 102 aft from the inlet duct 160. An outlet duct 164having an outlet nozzle 165 is within the main body 102 aft from thepropulsor 162. The aerial vehicle 100 has a center of gravity 166proximate to the propulsor 162.

In at least one embodiment, the inlet duct 160, portions of thepropulsor 162, and/or the outlet duct 164 are formed of, or otherwiselined with, acoustic devices and/or treatments that are configured tosuppress noise. For example, the inlet duct 160, portions of thepropulsor 162, and/or the outlet duct 164 can be or otherwise includefrequency-tailored Helmholtz resonator ducting, such as may be formedvia additive manufacturing.

The wings 118 include the control surfaces 130, such as aileron flaps168. The canards 136 also include control surfaces 131, such aselevators 170.

The main body 102 can also include an internal chamber 172. The internalchamber 172 can be accessed through a door, for example. The internalchamber 172 provides a space of volume for payload, for example.Alternatively, the main body 102 does not include the internal chamber172.

Battery packs 174 can be disposed within the wings 118. The batterypacks 174 provide power for operation of the control surfaces 130, forexample. Further, servos 176 can be secured within the wings 118. Theservos 176 operatively couple to the control surfaces 130 and can bepowered via the battery packs 174.

FIG. 9 illustrates a lateral transparent view of the aerial vehicle 100.The main body 102 can include a forward battery pack 180 and an aftbattery pack 182. The battery packs 180 and 182 are configured toprovide operational power.

FIG. 10 illustrates a cross-sectional view of the aerial vehicle throughline 10-10 of FIG. 2. The inlet 138 is in fluid communication with theinlet duct 160. The inlet 138 provides a fluid opening into the inletduct 160. The inlet duct 160 has an inlet height 190 proximate to theinlet 138 and an outlet height 192 proximate to the propulsor 162. Theinlet height 190 is less than the outlet height 192. The height of theinlet duct 160 increases from the inlet 138 toward the propulsor 162.Referring to FIGS. 8 and 10, the width 193 of the inlet duct 160decreases from the inlet 138 toward the propulsor 162. The inlet duct160 can be sized and shaped as indicated to provide space for theinternal chamber 172.

The outlet duct 164 has an inlet height 194 proximate to the propulsor162 and an outlet height 196 proximate to the outlet nozzle 165. Theinlet height 194 is greater than the outlet height 196. The height ofthe outlet duct 164 decreases from the propulsor 162 toward the outletnozzle 165. Referring to FIGS. 8 and 10, the width 195 of the outletduct 164 increased from the propulsor toward the outlet nozzle 165. Theoutlet duct 164 can be sized and shaped as indicated to provide spacefor the internal chamber 172.

FIG. 11 illustrates a cross-sectional view of the aerial vehicle 100through line 11-11 of FIG. 2. As shown, the propulsor 162 may not becoaxial with the longitudinal axis 122. Instead, the propulsor 162 canbe offset from the longitudinal axis 122, so as to provide room for theinternal chamber 172 (shown in FIG. 8).

FIG. 12 illustrates a cross-sectional view of the aerial vehicle throughline 12-12 of FIG. 2. As shown, the outlet duct 164 may not be coaxialwith the longitudinal axis 122. Instead, the outlet duct 164 can beoffset from the longitudinal axis 122, so as to provide room for theinternal chamber 172 (shown in FIG. 8).

Referring to FIGS. 1-12, the aerial vehicle 100 is configured to providea quiet configuration. The inlet 138 is in fluid communication with theoutlet nozzle 165 via the inlet duct 160, the propulsor 162, and theoutlet duct 164. The inlet 138 provides an air opening into the inletduct 160. The outlet nozzle 165 provides a fluid outlet from the outletduct 164. Noise emanating from the inlet 138 is reduced when the aerialvehicle is in an upright position (that is, when the top wall 112 isabove the base 108). In at least one embodiment, the aerial vehicle 100is a UAV.

The main body 102 can be flattened. For example, the top wall 112includes the flat upper surface 116, and the base 108 includes the flatlower surface 117. In at least one embodiment, the inlet 138 is disposedat a flattened, forward upper surface of the main body 102.

In at least one embodiment, the aerial vehicle 100 includes the mainbody 102 having the inlet 138, such as extending upwardly from the flatforward upper surface 109 of the base 108. The inlet 138 is in fluidcommunication with the outlet nozzle 165 at the aft end 106. The inlet138 is recessed aft from the leading edge 146 of the main body 102 andis bounded on either side by the forward protrusions 142. Wings 118extend from the main body 102. Noise emanating from the inlet 138 to theground is reduced when the aerial vehicle 100 is in the uprightposition.

It has been discovered that the embodiments of the subject disclosuredescribed herein provide aerial vehicles, such as UAVs, that generateless acoustic noise as detected from the ground.

FIG. 13 illustrates a flow chart of a method of forming an aerialvehicle, according to an embodiment of the subject disclosure. Themethod includes recessing, at 200, an inlet aft from a leading edge of amain body; extending, at 202, forward protrusions from the main body onopposite sides of the inlet; fluidly coupling, at 204, an outlet nozzleproximate to an aft end of the main body to the inlet; and extending, at206, wings from the main body.

In at least one embodiment, the method also includes extending the inletupwardly from a flat forward supper surface of a base of the main body.In at least one embodiment, the method also includes extending canardsfrom a fore end of the main body.

Further, the disclosure comprises embodiments according to the followingclauses:

Clause 1. An aerial vehicle comprising:

a main body having a leading edge,

an inlet recessed aft from the leading edge;

forward protrusions extending from the main body on opposite sides ofthe inlet;

an outlet nozzle proximate to an aft end of the main body, wherein theinlet is in fluid communication with the outlet nozzle; and

wings extending from the main body.

Clause 2. The aerial vehicle of Clause 1, wherein the aerial vehicle isan unmanned aerial vehicle (UAV).

Clause 3. The aerial vehicle of Clauses 1 or 2, wherein the main bodycomprises a base having a flat forward upper surface, wherein the inletextends upwardly from the flat forward upper surface.

Clause 4. The aerial vehicle of any of Clauses 1-3, further comprisingcanards extending from a fore end of the main body, and wherein thewings extend from the aft end of the main body.

Clause 5. The aerial vehicle of Clause 4, wherein at least portions ofthe canards extend to a plane that is aft of the inlet.

Clause 6. The aerial vehicle of any of Clauses 1-5, wherein at least oneof the forward protrusions extends either above or below a height of theinlet.

Clause 7. The aerial vehicle of any of Clauses 1-6, wherein the forwardprotrusions form a funneling entrance to the inlet.

Clause 8. The aerial vehicle of any of Clauses 1-7, wherein the inlethas a width and a height, wherein an aspect ratio is defined as a ratioof the width to the height, and wherein the aspect ratio is between 3and 7.

Clause 9. The aerial vehicle of Clause 8, wherein the aspect ratio isbetween 4.9 and 5.1.

Clause 10. The aerial vehicle of any of Clauses 1-9, wherein the inletis recessed from the leading edge a distance that is between 1 to 5times a height of the inlet.

Clause 11. The aerial vehicle of Clause 10, wherein the distance isbetween 2.9 and 3.0 times the height of the inlet.

Clause 12. The aerial vehicle of any of Clauses 1-11, furthercomprising:

an inlet duct within the main body, wherein the inlet provides anopening into the inlet duct;

a propulsor within the main body and in fluid communication with theinlet duct; and

an outlet duct within the main body and in fluid communication with thepropulsor, wherein the outlet duct includes the outlet nozzle.

Clause 13. A method of forming an aerial vehicle, the method comprising:

recessing an inlet aft from a leading edge of a main body;

extending forward protrusions from the main body on opposite sides ofthe inlet;

fluidly coupling an outlet nozzle proximate to an aft end of the mainbody to the inlet; and

extending wings from the main body.

Clause 14. The method of Clause 13, further comprising extending theinlet upwardly from a flat forward supper surface of a base of the mainbody.

Clause 15. The method of Clauses 13 or 14, further comprising extendingcanards from a fore end of the main body, and wherein the wings extendfrom the aft end of the main body.

Clause 16. The method Clause 15, wherein at least portions of thecanards extend to a plane that is aft of the inlet.

Clause 17. The method of any of Clauses 13-16, wherein at least one ofthe forward protrusions extends either above or below a height of theinlet, wherein the forward protrusions form a funneling entrance to theinlet.

Clause 18. The method of any of Clauses 13-17, wherein the inlet has awidth and a height, wherein an aspect ratio is defined as a ratio of thewidth to the height, and wherein the aspect ratio is between 3 and 7.

Clause 19. The method of any of Clauses 13-18, wherein the inlet isrecessed from the leading edge a distance that is between 1 to 5 times aheight of the inlet.

Clause 20. An unmanned aerial vehicle (UAV) comprising:

a main body having a leading edge, wherein the main body comprises abase having a flat forward upper surface;

an inlet recessed aft from the leading edge a distance that is between 1to 5 times a height of the inlet, wherein the inlet extends upwardlyfrom the flat forward upper surface, wherein an aspect ratio is definedas a ratio of a width to the height of the inlet, and wherein the aspectratio is between 3 and 7;

forward protrusions extending from the main body on opposite sides ofthe inlet, wherein at least one of the forward protrusions extendseither above or below a height of the inlet, and wherein the forwardprotrusions form a funneling entrance to the inlet;

an outlet nozzle proximate to an aft end of the main body, wherein theinlet is in fluid communication with the outlet nozzle;

wings extending from the aft end of the main body; and

canards extending from a fore end of the main body, wherein at leastportions of the canards extend to a plane that is aft of the inlet.

As described herein, embodiments of the present disclosure provide a UAVthat generates less noise than known UAVs. Further, embodiments of thepresent disclosure provide a UAV that quietly operates with reducedacoustic transmissions to the ground below.

While various spatial and directional terms, such as top, bottom, lower,mid, lateral, horizontal, vertical, front and the like can be used todescribe embodiments of the subject disclosure, it is understood thatsuch terms are merely used with respect to the orientations shown in thedrawings. The orientations can be inverted, rotated, or otherwisechanged, such that an upper portion is a lower portion, and vice versa,horizontal becomes vertical, and the like.

As used herein, a structure, limitation, or element that is “configuredto” perform a task or operation is particularly structurally formed,constructed, or adapted in a manner corresponding to the task oroperation. For purposes of clarity and the avoidance of doubt, an objectthat is merely capable of being modified to perform the task oroperation is not “configured to” perform the task or operation as usedherein.

It is to be understood that the above description is intended to beillustrative, and not restrictive. For example, the above-describedembodiments (and/or aspects thereof) can be used in combination witheach other. In addition, many modifications can be made to adapt aparticular situation or material to the teachings of the variousembodiments of the disclosure without departing from their scope. Whilethe dimensions and types of materials described herein are intended todefine the parameters of the various embodiments of the disclosure, theembodiments are by no means limiting and are exemplary embodiments. Manyother embodiments will be apparent to those of skill in the art uponreviewing the above description. The scope of the various embodiments ofthe disclosure should, therefore, be determined with reference to theappended claims, along with the full scope of equivalents to which suchclaims are entitled. In the appended claims and the detailed descriptionherein, the terms “including” and “containing” are used as theplain-English equivalents of the term “comprising” and the term “inwhich” is used as the plain-English equivalents of the term “wherein.”Moreover, the terms “first,” “second,” and “third,” etc. are used merelyas labels, and are not intended to impose numerical requirements ontheir objects. Further, the limitations of the following claims are notwritten in means-plus-function format and are not intended to beinterpreted based on 35 U.S.C. § 112(f), unless and until such claimlimitations expressly use the phrase “means for” followed by a statementof function void of further structure.

This written description uses examples to disclose the variousembodiments of the disclosure, including the best mode, and also toenable any person skilled in the art to practice the various embodimentsof the disclosure, including making and using any devices or systems andperforming any incorporated methods. The patentable scope of the variousembodiments of the disclosure is defined by the claims, and can includeother examples that occur to those skilled in the art. Such otherexamples are intended to be within the scope of the claims if theexamples have structural elements that do not differ from the literallanguage of the claims, or if the examples include equivalent structuralelements with insubstantial differences from the literal language of theclaims.

What is claimed is:
 1. An aerial vehicle comprising: a main body havinga leading edge, an inlet recessed aft from the leading edge; forwardprotrusions extending from the main body on opposite sides of the inlet;an outlet nozzle proximate to an aft end of the main body, wherein theinlet is in fluid communication with the outlet nozzle; and wingsextending from the main body.
 2. The aerial vehicle of claim 1, whereinthe aerial vehicle is an unmanned aerial vehicle (UAV).
 3. The aerialvehicle of claim 1, wherein the main body comprises a base having a flatforward upper surface, wherein the inlet extends upwardly from the flatforward upper surface.
 4. The aerial vehicle of claim 1, furthercomprising canards extending from a fore end of the main body, andwherein the wings extend from the aft end of the main body.
 5. Theaerial vehicle of claim 4, wherein at least portions of the canardsextend to a plane that is aft of the inlet.
 6. The aerial vehicle ofclaim 1, wherein at least one of the forward protrusions extends eitherabove or below a height of the inlet.
 7. The aerial vehicle of claim 1,wherein the forward protrusions form a funneling entrance to the inlet.8. The aerial vehicle of claim 1, wherein the inlet has a width and aheight, wherein an aspect ratio is defined as a ratio of the width tothe height, and wherein the aspect ratio is between 3 and
 7. 9. Theaerial vehicle of claim 8, wherein the aspect ratio is between 4.9 and5.1.
 10. The aerial vehicle of claim 1, wherein the inlet is recessedfrom the leading edge a distance that is between 1 to 5 times a heightof the inlet.
 11. The aerial vehicle of claim 10, wherein the distanceis between 2.9 and 3.0 times the height of the inlet.
 12. The aerialvehicle of claim 1, further comprising: an inlet duct within the mainbody, wherein the inlet provides an opening into the inlet duct; apropulsor within the main body and in fluid communication with the inletduct; and an outlet duct within the main body and in fluid communicationwith the propulsor, wherein the outlet duct includes the outlet nozzle.13. A method of forming an aerial vehicle, the method comprising:recessing an inlet aft from a leading edge of a main body; extendingforward protrusions from the main body on opposite sides of the inlet;fluidly coupling an outlet nozzle proximate to an aft end of the mainbody to the inlet; and extending wings from the main body.
 14. Themethod of claim 13, further comprising extending the inlet upwardly froma flat forward supper surface of a base of the main body.
 15. The methodof claim 13, further comprising extending canards from a fore end of themain body, and wherein the wings extend from the aft end of the mainbody.
 16. The method of claim 15, wherein at least portions of thecanards extend to a plane that is aft of the inlet.
 17. The method ofclaim 13, wherein at least one of the forward protrusions extends eitherabove or below a height of the inlet, wherein the forward protrusionsform a funneling entrance to the inlet.
 18. The method of claim 13,wherein the inlet has a width and a height, wherein an aspect ratio isdefined as a ratio of the width to the height, and wherein the aspectratio is between 3 and
 7. 19. The method of claim 13, wherein the inletis recessed from the leading edge a distance that is between 1 to 5times a height of the inlet.
 20. An unmanned aerial vehicle (UAV)comprising: a main body having a leading edge, wherein the main bodycomprises a base having a flat forward upper surface; an inlet recessedaft from the leading edge a distance that is between 1 to 5 times aheight of the inlet, wherein the inlet extends upwardly from the flatforward upper surface, wherein an aspect ratio is defined as a ratio ofa width to the height of the inlet, and wherein the aspect ratio isbetween 3 and 7; forward protrusions extending from the main body onopposite sides of the inlet, wherein at least one of the forwardprotrusions extends either above or below a height of the inlet, andwherein the forward protrusions form a funneling entrance to the inlet;an outlet nozzle proximate to an aft end of the main body, wherein theinlet is in fluid communication with the outlet nozzle; wings extendingfrom the aft end of the main body; and canards extending from a fore endof the main body, wherein at least portions of the canards extend to aplane that is aft of the inlet.